MECANISME DE VERROUILLAGE D'ATTERRISSEUR D'AERONEF

AIRCRAFT UNDERCARRIAGE LOCK MECHANISM

Abrégé français

L'invention concerne un mécanisme (20) pour atterrisseur d'aéronef, comprenant un premier élément de verrouillage (22) monté sur l'atterrisseur (14), venant en prise avec un deuxième élément de verrouillage (24) monté sur une aile (10) de l'aéronef. Le premier élément de verrouillage (22) se compose d'un bras pivotant (26) qui porte un galet (36), lequel (36) est rotatif et coulissant sur le bras (26) et vient en prise avec un cliquet (48) prévu sur le deuxième élément de verrouillage (24). Le bras pivotant (269 et le galet coulissant (36) permettent un mouvement relatif entre les éléments de verrouillage (22, 24) lorsque l'atterrisseur (14) est rentré et que les éléments de verrouillage sont en prise de manière à minimiser la transmission des forces induites par la déflexion de l'aile d'un élément de verrouillage à l'autre.

Abrégé anglais

An aircraft undercarriage mechanism (20) comprising a first lock member (22)
mounted on the undercarriage (14), the first lock member being engageable with
a second lock member (24) mounted on a wing (10) of the aircraft. The first
lock member (22) comprises a pivotable arm (26) which carries a roller (36).
The roller (36) is rotatable and slidable on the arm (26) and is engageable
with a catch (48) on the second lock member (24). The provision of the
pivotable arm (26) and slidable roller (36) permits relative movement between
the lock members (22, 24) when the undercarriage (14) is retracted with the
lock members interengaged to minimise transmission of forces created by wing
deflection from one lock member to the other.

Revendications

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CLAIMS
1 An aircraft undercarriage mechanism comprising a first lock member (22) for
mounting on the undercarriage (14) or on an undercarriage door (16), the first
lock
member (22) being engageable with a second lock member (24) for mounting on a
support part (10) of the aircraft, such that when the undercarriage (14) is
retracted
with the lock members (22,24) interengaged relative movement can take place
between said lock members (22,24) in a first direction, characterised in that
one of
said lock members (22) has an element (36) movably mounted on a part thereof
to
permit further relative movement between the first and second lock members
(22,24)
in a direction transverse to the said first direction when the undercarriage
(14) is
retracted with the lock members (22,24) engaged to minimise transmission of
forces
created by wing deflection from one lock member (22) to the other (24).
2 An aircraft undercarriage mechanism according to claim 1 in which the
element (36) is roller.
3 An aircraft undercarriage mechanism according to claim 1 or 2 in which
alignment means (52) is provided for receiving and positioning the element
(36)on
said part of the one lock member during closing of the undercarriage door (16)
4 An aircraft undercarriage mechanism according to claim 1, 2 or 3 installed
in
an aircraft, the first lock member (22) being mounted on the undercarriage
door (16)
and the second lock member (24) being mounted on the support part (10) of the
aircraft, and being arranged to engage the second lock member (24) when the
undercarriage door (16) is closed.
An aircraft undercarriage mechanism according to any of claims 1 to 3
installed in an aircraft, the first lock member (22) being mounted on a leg
(13) of
the undercarriage (14) and being arranged to engage the second lock member
(24)
when the undercarriage (14) is retracted.

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6 An aircraft undercarriage mechanism according to any preceding claim in
which said one lock member (22) is mounted on the undercarriage (14).
7 An aircraft undercarriage mechanism according to any preceding claim in
which the support part (10) of the aircraft is part of a wing of the aircraft.

Description

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AIRCRAFT UNDERCARRIAGE MECHANISM
The invention relates to an aircraft undercarriage mechanism. The invention is
to be applied primarily to an aircraft wing landing gear door which must
remain
safely closed when the landing gear wheels are retained in a wheel bay during
s flight.
Typically, an undercarriage door is held closed by a locking mechanism
comprising a catch and a member engageable with the catch, one of which
member and catch is arranged on the undercarriage door and the other of
io which is arranged on part of the wing. Aircraft wings deflect during flight
as
various forces acting on the wings vary in magnitude. Such deflection can
cause relative movement to occur between the door and the wing which, in
turn, transmits force to the locking mechanism which can be a problem and an
object of the invention is to provide a door locking mechanism which minimises
is that problem. EP-A- 0 265 197 discloses an aircraft undercarriage where a
locking
mechanism permits relative rocking movement to take place in a single plane
between parts of the mechanism when the undercarriage is locked in a retracted
position so that the locking mechanism is relatively immune to the effects of
air
frame deflection.
According to an aspect of the present invention there is provided an aircraft
undercarriage mechanism comprising a first lock member for mounting on the
undercarriage or on an undercarriage door, the first lock member being
engageable
with a second lock member for mounting on a support part of the aircraft, such
that
2s when the undercarriage is retracted with the lock members interengaged
relative
movement can take place between said lock members in a first direction,
characterised in that one of said lock members has an element movably mounted
on
a part thereof to permit further relative movement between the first and
second lock
members in a direction transverse to the said first direction when the
undercarriage
AMENDED SHEET

27-11-2000 ~ ~ CA 02361921 2001-08-O1 GB 000000292
- J.a -
is retracted with the lock ri~embers engaged to minimise transmission of
forces
created by wing deflection from one lock member to the other.
Where wing deflection is, say, of a combined bending and torsional kind, the
s movement of the interengaged lock member will preferably accommodate
both kinds of deflection.
AMENDED SHEET

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Preferably, the said means comprises an element movably mounted on the
one lock member. In such a case, the element may be slidable and/or
rotatable on the one lock member. In that way, the other lock member may
remain interengaged with the element while the one lock member having the
element thereon is able to move relative to the element. The element may
conveniently take the form of a roller.
Preferably, alignment means is provided for receiving and positioning the
to element relative to the other lock member during closing of the door. That
allows the element to be moved into an optimum position before the lock
members interengage. In such a case, the alignment means may have a cam
surface which is arranged to position the element. The alignment means may
limit the frictional loads which would, in its absence, be transmitted to the
Is other lock member. The alignment means may comprise a fork which
receives and positions the element. The alignment means is preferably
arranged to hold the element in its aligned position. The element may be
received in a recess defined by part of the alignment means.
?o In a preferred embodiment, the one lock member is in the form of an arm
which may be pivotally connected to its mounting at one of its ends. Where a
said element is provided, the element may be slidably mounted on an opposite
end of the arm. The first lock member may be mounted on a door or leg of the
undercarriage.
?s
Preferably, said one lock member is mounted on the undercarriage.

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CVO 00/48903 3 PCT/GB00/00292
According to a second aspect of the invention there is provided an aircraft
undercarriage including a mechanism according to the first said aspect of the
invention or any of the consistory clauses relating thereto.
According to another aspect of the invention there is provided an aircraft
having an undercarriage mechanism according to the first said aspect of the
invention or any of the consistory clauses relating thereto.
An aircraft undercarriage door locking mechanism in accordance with the
Io present invention will now be described by way of example and with
reference
to the accompanying drawings, in which:
Fig 1 is a diagrammatic cross-section taken chord-wise through an
aircraft wing showing a known type of undercarriage door in a closed
is position,
Fig 2 is a perspective view of the aircraft undercarriage mechanism in
accordance with the invention showing first and second locking members
immediately prior to interengagement,
Fig 3 illustrates the said first lock member mounted on an undercarriage
door,
Fig 4 is a perspective view of the locking mechanism in accordance with
2s the invention showing the lock members interengaged but with an
alignment fork omitted for clarity,
Fig 5 shows the first lock member engaged with an alignment fork and
viewed from one side, and

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WO 00/48903 4 PCT/GB00/00292
Fig 6 is similar to Fig 5 and viewed from an opposite side.
Referring to Fig 1, an aircraft wing 10 is constructed to define an
undercarriage
s wheel bay 12 in which a leg 13 of an undercarriage 14 (shown in broken
lines)
is stowed during flight. Once the undercarriage leg 13 is in its stowed
position,
the wheel bay 12 is closed by means of a door 16 of the undercarriage which
is attached to the wing 10 by a hinge 18. The door 16 may be closed by
associated hydraulics or may be moved into its closed position by the
io movement of the undercarriage 14 into its stowed position. Once the door 16
has reached its closed position, it is held closed by an undercarriage
mechanism 20. The mechanism 20 comprises a first lock member 22 on the
door 16 and a second lock member 24 on the wing 10. The lock members 22,
24 interengage to hold the door 16 closed. When the undercarriage 14 is to be
is Ibwered, the lock members 22, 24 are disengaged. Deflection of the wing 10,
e.g. bending and/or twisting, causes the door 16 to move relative to the wing
which, in turn, transmits load to the mechanism 20. Therefore, the
mechanism 20 has to be made sufficiently robust in order to tolerate such
extra forces and, from the point of view of weight, that is not desirable.
?o
Looking at Fig 2, the first lock member 22 in accordance with the invention is
in the form of an arm 26 connected to a base 28 by means of a pivot bolt 30
which passes through side sections 27 of the arm 26. The base 28 is mounted
on the undercarriage door 16 by fasteners (not shown) which locate in
Zs apertures 32 in the base 28 (see Fig 3). A further bolt 34 is passed
through the
free ends of the side sections 27 and supports a hollow roller 36 which is
rotatable on the further bolt 34. The length of the roller 36 is less than the
distance between the two spaced apart side sections 27 to allow the roller 36
to slide axially on the further bolt 34, that is in the directions of arrows
A. The

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two bolts 30, 34 are hollow and have radial outlets through which grease
(supplied to nipples 30a, 34a on the~bolts) can be distributed.
Looking at Fig 3, the roller 36 has first and second ends 38, 40 and has
thereon first and second spaced apart fixed collars 42, 44. A section 46
between the first end 38 and the first collar 42 is engageable with a catch 48
on the second lock member 24 and a space 50 between the first and second
collars 42, 44 is received by an alignment fork 52 as the door 16 moves
towards its closed position in the direction of arrow B in Fig 2.
io
The fork 52 is fixed to the wing 10 adjacent the second lock member 24. The
fork 52 is a single component having arms 54 which are joined at their upper
ends, as viewed in Fig 2, by mounting 56 which defines a semi-cylindrical
recess 57. The mounting 56 has side flanges 58 by which it can be attached
i~ to the wing 10 using suitable fasteners which locate in apertures 59 in the
flanges 58 shown in Fig 6.
As shown in Fig 5, the arms 54 have respective inside faces 60 which diverge
in a direction away from the mounting 56. Each of the arms 54 also has two
?o side faces 62, 64 which converge in a direction away from the mounting. The
inside faces 60 of the fork 52 serve to capture the roller 36 by entering the
space 50 between the collars 42, 44 as shown in Fig 2 as the door 16 is
moved towards its closed position.
?s The side faces 62 serve to position the roller 36 axially on the further
bolt 34. If
the roller 36 is positioned too far to the left as viewed in Fig 2, the side
faces
62 will act as cams on the collar 42 to urge the roller to the right. If the
roller 36
is positioned too far to the right as viewed in Fig 2, the side faces 64 will
act as

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cams on the collar 44 to urge the roller to the left. In that way, the fork 52
correctly aligns the section 46 of the roller 36 with the catch 48.
Each of the arms 54 has further side faces 66 which are parallel and extend
s between the upper ends of the side faces 64 and the interior of the recess
57.
The side faces 66 of each arm 54 are spaced apart by a distance which
enables the side faces 66 to fit between the two collars 42, 44 with only
slight
working clearance.
to As illustrated in Fig 2 and when the undercarriage mechanism 20 is not
engaged, the arm 26 projects from the door 16 in anticipation of engagement
between the roller 36 and the catch 48. A suitable stop arrangement (not
shown) is provided on the base 28 to limit the amount of pivotal movement of
the arm 26 about the pivot bolt 30. In that way, the arm 26 will be unable to
is pivot into a position where the roller 36 cannot be located by the fork 52.
As
the door 16 is almost closed the fork 52 receives the roller 36 and aligns the
section 46 with the catch 48, the roller entering the recess 57 with the side
surfaces 66 of the arms 54 between the collars 42, 44 to hold the roller 36 in
the aligned position. A clearance c at the top of the recess 57 prevents the
?o collar 44 from contacting the top of the recess 57. The catch 48 finally
engages the section 46 to hold the door 16 closed i.e. the vertical stop is
the
catch 48. The catch 48 moves to engage the roller 36 in known manner.
Once the aircraft is airborne with the door 16 closed, the wing 10 will
deflect as
?s a result of forces acting thereon typically resulting in bending and
twisting of
the wing 10. The pivotal mounting of the arm 26 enables the wing 10 and the
door 16 to move relative to each other as a result of twisting movement of the
wing 10. Such relative movement causes the side sections 27 to pivot on the
bolt 30 and relative to the roller 36. In that way, twisting movement of the
wing

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does not create any significant extra loading on the catch 48. By slidably
mounting the roller 36 on the further bolt 34, movement of the door 16
relative
to the wing 10 resulting from bending of the wing, will enable the further
bolt 34
to slide axially within the roller 36 again without creating any significant
extra
s loading on the catch 48. In that way any frictional loads caused by sliding
motion of roller 36 on bolt 34 and pivoting of side sections 27 on bolt 30,
are
transmitted through the form 52, limiting the side loading applied to the
catch
48.
io It will be appreciated that combined twisting and bending movement of the
wing 10 can be accommodated by the undercarriage mechanism 20 of the
invention.
Although the invention is described as being applied to an aircraft wing
is undercarriage door it could also be used to secure the aircraft
undercarriage
leg 13. In such a case the first lock member 22 is carried by the leg 13.

Dessin représentatif